CN103703227A - Aircraft control and monitoring system - Google Patents
Aircraft control and monitoring system Download PDFInfo
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- CN103703227A CN103703227A CN201280035557.8A CN201280035557A CN103703227A CN 103703227 A CN103703227 A CN 103703227A CN 201280035557 A CN201280035557 A CN 201280035557A CN 103703227 A CN103703227 A CN 103703227A
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- temperature information
- temperature
- acquisition channel
- data processing
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
- F02C9/16—Control of working fluid flow
- F02C9/18—Control of working fluid flow by bleeding, bypassing or acting on variable working fluid interconnections between turbines or compressors or their stages
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C6/00—Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas- turbine plants for special use
- F02C6/04—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output
- F02C6/06—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output providing compressed gas
- F02C6/08—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output providing compressed gas the gas being bled from the gas-turbine compressor
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2270/00—Control
- F05D2270/30—Control parameters, e.g. input parameters
- F05D2270/303—Temperature
Abstract
The invention relates to a system for bleeding air on an aircraft, comprising: at least one air bleed valve (5, 5', 5") that can bleed a flow (F) of air on the aircraft, a first temperature information module (10), a second temperature information module (20), at least one control module (30), and at least one data processing module (40) coupled to the control module (30).
Description
Technical field
The present invention relates to the system and method for control & monitor aircraft, more specifically relate to a kind of in aircraft for controlling the temperature of gas discharging, with for monitoring the system surpassing of predetermined temperature threshold.
Background technique
Known aircraft, for example aircraft, comprises fuselage, this fuselage comprises cockpit panel, passenger compartment and at least one engine group.Such engine group comprises an engine and a fan, and gas discharging can be formed by this fan.Such discharge is produced by a system, and this system is called gas blow-off system, comprises a plurality of valves and a precooler.These valves make can switch gas in this engine or in the different air-flows of this engine circulation around, described air-flow is high pressure, the high temperature gas flow for flowing out on engine for example, same middle pressure, the low-temperature airflow flowing out on engine, and the fan cold airflow flowing out on fan.Air-flow under high pressure and in the air-flow depressed can be mixed into the mixed flow that is supplied to this precooler.This precooler is subsequently for the heat exchange between described mixed flow and fan airstream, makes to be reduced in the temperature of the mixed flow in this precooler outlet port, will have through regulating the air-flow of temperature to be fed to for example cockpit or the passenger compartment of aircraft.
Such adjusting by control one or more described air-flow escape cocks open obtain.The temperature of air-flow can be by the selection of controlled one or more valves, for example by control fan airstream escape cock open or close regulate.
Known a kind of system, wherein, on the one hand, controls temperature, so that one or more valve can open or close; On the other hand, carry out whether surpassing the supervision of a predetermined temperature threshold, think closing of one or more valves (for example hot discharge gas valve), or opening of one or more valve (for example cold air escape cock) prepare, in case described threshold value is exceeded.While for example occurring in surpassing like this excess Temperature when the eluting gas for cockpit, this accidental event is classified as the catastrophic event about aircraft security aspect.
Known gas blow-off system comprises a duct thermostat, and it is directly connected with one or more valves, and makes on described valve, to control the temperature of gas discharging, and opening by this duct thermostat signal of valve or a plurality of valves adjusted.Yet such duct thermostat can cause thermometry inaccurate, therefore, extend ground, their control is also inaccurate.
An existing scheme, for placing a temperature transducer, to measure the temperature from the air-flow of this precooler, and is given a gas blow-off system supervisory computer for this gas blow-off system by this measurement report.This measurement result in good time obtaining makes this computer can carry out the control of gas discharging temperature and the supervision of carrying out whether surpassing a predetermined temperature threshold by the temperature of this gas discharging subsequently.Yet the use of this kind of measurement causes sharing model problem.In fact, since control & monitor relies on identical measured temperature in the case simultaneously, incorrect measured value means the poor control of this gas discharging temperature and to whether, surpasses the poor supervision of a predetermined gas exhaust temperature threshold value, and it has the problem about aircraft security aspect.
Summary of the invention
The object of the invention is part and eliminate these shortcomings.For this reason, it relates to a kind of gas blow-off system of aircraft, and described system comprises:
-at least one gas emitting valve, it is suitable for discharging carry-on air-flow,
The-the first temperature information module, it is set to through one first Acquisition channel, and determine and send first row bleed flow temperature information,
The-the second temperature information module, it is set to through one second Acquisition channel, and determine and send second row bleed flow temperature information,
-at least one administration module, it is connected with a data processing module, and is set to:
-on the one hand, through the first Acquisition channel, receive described first row bleed flow temperature information, the gas emitting valve control that is a correspondence is prepared, and/or, on the other hand, through the second Acquisition channel, this second row bleed flow temperature information makes to monitor whether surpass a predetermined exhaust jet stream temperature threshold
-send described the first temperature information and the second temperature information,
-at least one data processing module, it is connected with described administration module, and is set to:
-through one first process course, receive described first row bleed flow temperature information, and be that the gas emitting valve of a correspondence is controlled and to be prepared,
-through one second process course, receive described second row bleed flow temperature information, make to monitor whether to surpass a predetermined exhaust jet stream temperature threshold, and at least one gas emitting valve can be closed in the situation that described threshold value is exceeded.
Term " discharges carry-on air-flow " and is interpreted as representing the action from the fan of for example aircraft or the airflow circulating eluting gas engine at this.
" Acquisition channel " is interpreted as representing a communication port, and it is suitable for for the transmission of the information being sent by an information module.
" process course " is interpreted as representing a communication port, and it is suitable for for communication to puocessing module, and a process course can be identical with an Acquisition channel, merges with an Acquisition channel.
The state that " temperature information " is interpreted as representing the measurement result of temperature or surpasses a temperature threshold.
The state that is interpreted as representing measurement temperature or surpasses a predetermined temperature threshold by the temperature foundation of exhaust jet stream " determined " in term.
" state that surpasses a temperature threshold " is interpreted as representing result binary or Boolean logic of " threshold value is exceeded " or " threshold value is not exceeded " type.One state can be a bi-values, or adopts for example form of centrifugal pump.
It should be noted that, a threshold value can be arranged on a given moment, but it can be modified subsequently, for example, make this module to reduce work pattern.
The temperature information that is received from administration module by data processing module for example can comprise according to a thermometric numerical value, or surpass the state of a predetermined temperature threshold.
Therefore such system makes both to control gas discharging temperature, and two temperature information projects based on obtaining through two different Acquisition channels monitor whether surpass a predetermined gas exhaust temperature threshold value again.In other words, first information module makes to obtain the first temperature information, and with execution control function, and the second information module makes to obtain the second temperature information, with execution monitoring function.Therefore, in control and between monitoring, no longer include any sharing model.And control & monitor carries out based on for example measurement result or over the such accurate temperature information of given state of predetermined temperature threshold.
Advantageously, this system comprises pressurized gas escape cock, medium pressure gas escape cock, fan gas emitting valve and precooler, exhaust jet stream on pressurized gas escape cock mixes with the exhaust jet stream on medium pressure gas escape cock, to obtain the mixed flow of this precooler ingress, this precooler be suitable for by with fan gas emitting valve on the air-flow that discharges carry out heat exchange and carry out again cooling described mixed flow.
Preferably, this the first temperature information module is set to through this first Acquisition channel, measure and transmit one first row bleed flow temperature measurement result, this the second temperature information module is set to through this second Acquisition channel, measure and transmit one second row bleed flow temperature measurement result, or through this second Acquisition channel, determine and send the temperature of this exhaust jet stream over the state of a predetermined temperature threshold.
According to feature of the present invention, this administration module comprises:
-analysis module, this analysis module is set to convert the measurement result of the temperature of exhaust jet stream to digital value and/or the information of the temperature of the described exhaust jet stream about received is compared with a predetermined threshold, and
-transmitting module, this transmitting module is set to send described digital value and/or comparing result.
Particularly, this administration module can be suitable for received analog temperature measurement result to be converted to spendable digital value by for example processor or field programmable gate array (FPGA).
Advantageously, this aircraft comprises a computer, and this administration module and data processing module are by described computer realization.A known computer comprises the message handler that is set to processing data and computer program.This computer can be the engine computer of for example aircraft, for the information of the engine running aspect of managing aircraft.The use of this aircraft engine computer makes to avoid this gas blow-off system for managing aircraft, therefore carries out with centralized system the gas blow-off system of this aircraft and the use to the extra computation machine of the control of engine.
According to a feature of the present invention, this the first temperature information module is set to through this first Acquisition channel, measure and transmit one first row bleed flow temperature measurement result, this the second temperature information module is set to through this second Acquisition channel, measure and transmit one second row bleed flow temperature measurement result, this administration module is suitable for from this first temperature information module, through this first Acquisition channel, receive described the first measurement result, and from this second temperature information module, through this second Acquisition channel, receive described the second measurement result, described administration module is connected with a puocessing module, described the first and second process course are identical.
Like this, this first information module makes to obtain one first temperature measurement result, to carry out described control function, and the second information module makes to obtain one second temperature measurement result, to carry out described function for monitoring, in this case, these two measurement results send to an independent puocessing module by this independent administration module, and they are by an independent lane interconnect.Like this, these two temperature information projects are separated until this administration module.
According to a feature of the present invention, this system also comprises one second administration module, this second administration module is connected with one second data processing module by the third and fourth same treatment passage, and on the one hand, be connected to described the first temperature information module, on the other hand, be connected to described the second temperature information module, this second administration module is suitable for through one the 3rd Acquisition channel, from this first temperature information module, receive this first measurement result, and through one the 4th Acquisition channel, from this second temperature information module, receive this second measurement result.
Such configuration makes for example on one first physical channel of for example computer, to merge first passage and second channel, each passage is all reported the temperature measurement result from a different temperatures information module (respectively from the first and second temperature information modules), and, on one second physical channel, merge first passage and second channel, each passage is all reported the temperature measurement result from a different temperatures information module (respectively from the first and second temperature information modules).The use of these two physical channels makes to divide the management function of this administration module, if so that in described administration module breaks down, another can guarantee its function.
According to another characteristic of the invention, this the first temperature information module is set to through described the first Acquisition channel, measure and transmit one first row bleed flow temperature measurement result, this the second temperature information module is set to through described the second Acquisition channel, determine and send the temperature of an exhaust jet stream over the state of a predetermined temperature threshold, this administration module is set to through described the first Acquisition channel, receive this temperature measurement result, through described the second Acquisition channel, receive and should surpass state, this first and second process course is identical.
Like this, this first information module makes to obtain a temperature measurement result, to carry out this control function, and this second information module makes to obtain the state that surpasses a predetermined temperature threshold, to carry out this function for monitoring, in this case, these two information projects send to an independent puocessing module by described independent administration module, and they are by an independent lane interconnect.
According to another characteristic of the invention, this the first temperature information module is set to through described the first Acquisition channel, measure and transmit one first row bleed flow temperature measurement result, this second information module is set to through described the second Acquisition channel, determine and send the temperature of an exhaust jet stream over the state of a predetermined temperature threshold, this administration module is set to through described the first Acquisition channel, receive this temperature measurement result, this data processing module is set to through described the second Acquisition channel, receive and should surpass state, described the second Acquisition channel and the second process course are identical.
Like this, this first information module makes to obtain a temperature measurement result, and to carry out described control function, and this second information module makes to obtain a state over a predetermined temperature threshold, to carry out described function for monitoring.In the case, only described measurement result sends to this independent administration module, and this state directly sends to described independent data processing module by this second information module.Like this, these two temperature information projects are separated until described data processing module.
According to another characteristic of the invention, this the first temperature information module is set to through described the first Acquisition channel, measure and transmit one first row bleed flow temperature measurement result, this the second temperature information module is set to through described the second Acquisition channel, determine and send the temperature of exhaust jet stream described in over the state of a predetermined temperature threshold, this administration module is set to through described the first Acquisition channel, receive described temperature measurement result, and through described the second Acquisition channel, receive the described state that surpasses, described the second Acquisition channel and described the second process course are different.
Like this, described first information module makes to obtain a temperature measurement result, and to carry out described control function, and described the second information module makes to obtain a state over a predetermined temperature threshold, to carry out described function for monitoring.In the case, these two temperature information projects are sent to described independent administration module, but this measurement result is sent to described independent puocessing module through one first process course, described state is sent to described independent data processing module through one second process course, and this makes these two temperature information projects separable until described data processing module.
According to another characteristic of the invention, this system comprises one first data processing module, and it is set to through described the first process course, receive described the first temperature information, with one second data processing module, it is set to, through described the second process course, receive described the second temperature information.
Like this, the control of gas discharging temperature and surpass the supervision of a predetermined gas exhaust temperature threshold value can be separated between two data processing modules, in other words, for example separated between two computers of aircraft, this make can in the situation that the fault of in the described computer of hypothesis only causes controlling or function for monitoring in a failure increase the safety of this aircraft.
According to another characteristic of the invention, described the second data processing module is set to described the second temperature information to send to described the first data processing module.This state can directly or for example send through a communication module.
According to another characteristic of the invention, this system also comprises one the 3rd data processing module, and the 3rd data processing module is set to, through one the 3rd process course, receive described the first temperature information.
This make can, by separating in described puocessing module, ensure to obtain this first temperature information.
The invention still further relates to that a kind of described aircraft comprises the gas blow-off system of aircraft for managing the method at the gas blow-off system of aircraft, described system comprises:
-at least one gas emitting valve, this gas emitting valve is suitable for discharging this carry-on air-flow,
The-the first temperature information module, this first temperature information module is set to through one first Acquisition channel, and determine and send first row bleed flow temperature information,
The-the second temperature information module, this second temperature information module is set to through one second Acquisition channel, and determine and send second row bleed flow temperature information,
-at least one administration module, this administration module is connected with a data processing module, and is set to:
-on the one hand, through this first Acquisition channel, receive this first row bleed flow temperature information, for corresponding gas emitting valve, control, and/or, on the other hand, through this second Acquisition channel, receive this second row bleed flow temperature information, make to monitor whether surpass a predetermined exhaust jet stream temperature threshold
-send this first temperature information and this second temperature information,
-at least one data processing module, this data processing module is connected with described administration module, and is set to:
-through one first process course, receive described first row bleed flow temperature information, and control for corresponding gas emitting valve,
-through one second process course, receive described second row bleed flow temperature information, make to monitor whether surpass a predetermined exhaust jet stream temperature threshold, and for close at least one gas emitting valve in the situation that described threshold value is exceeded,
The method comprises the following steps:
-be disposed to the air-flow on valve described in small part,
-on described administration module, receive this first temperature information from the described exhaust jet stream of described the first temperature information module,
-on described administration module or described data processing module, receive this second temperature information from the described exhaust jet stream of described the second temperature information module,
-on described data processing module, receive described the first temperature information and/or the second temperature information,
-according to described the first temperature information and/or the second temperature information, on described data processing module, control opening or closing of one or more gas emitting valves.
Accompanying drawing explanation
By read the following description of one embodiment of the invention with reference to respective figure (identical reference character relates to similar object), it is clearer that the features and advantages of the invention will become, wherein:
Fig. 1 a shows according to system of the present invention,
Fig. 1 b shows according to the first embodiment of system of the present invention,
Fig. 1 c shows according to the second embodiment of system of the present invention,
Fig. 2 shows according to the 3rd embodiment of system of the present invention,
Fig. 3 shows according to the 4th embodiment of system of the present invention,
Fig. 4 shows according to the 5th embodiment of system of the present invention,
Fig. 5 shows according to the 6th embodiment of system of the present invention,
Fig. 6 shows according to the 7th embodiment of system of the present invention.
Embodiment
According to system of the present invention, about temperature measurement result or the state that surpasses a predetermined temperature threshold, be described hereinbefore.Yet, it should be noted that, the present invention also can be applicable to other such measurements of for example pressure measurement, or is applied to surpass the state of a predetermined pressure threshold, so that, similarly, the open and/or closed of the valve of the gas blow-off system of control aircraft.
Fig. 1 a shows according to the gas blow-off system 1 of aircraft of the present invention, comprises two gas emitting valves 5 and 5 ' in the air-flow of engine 2 cocycles of this aircraft, and two gas emitting valves 5 of the stream of the fan cocycle of the described engine 2 of this aircraft ".
This valve 5 can be for example the escape cock in the air-flow in middle pressure discharging on an engine, and valve 5 ' can be for example the escape cock in the air-flow in high pressure of the higher temperature that also discharges on this engine.Valve 5 " make a cold airflow directly can be discharged on the fan of engine 2 upstreams of this aircraft.
By the air-flow of gas emitting valve 5, the 5 ' discharge on this engine, be mixed into the mixed flow of precooler 6 upstreams.This precooler is for the heat exchange between above-mentioned mixed flow and this fan airstream, makes to be reduced in the temperature of this mixed flow F obtaining in described precooler outlet port.This,, through regulating the resulting mixed flow F of temperature by pipeline 7 guiding, for example, through a gas regulating system, to this cockpit or passenger compartment, or is wing deicing.
Such adjusting is by controlling one or more air- flow escape cocks 5,5 ', 5 " open obtain.Particularly, the temperature of this air-flow can be by controlling fan airstream escape cock 5 " open or close, or by selecting controlled valve or a plurality of valve 5,5 ', 5 " regulate.
This system 1 also comprises the first temperature information module 10, the second temperature information module 20, at least one administration module 30 and at least one data processing module 40 being connected with described administration module 30.
This first temperature information module 10 is set to through one first Acquisition channel 15, the first temperature measurement result of the exhaust jet stream F of circulation in measure and transmit pipeline 7.
This second temperature information module 20 is set to through one second Acquisition channel 25, the second temperature measurement result of the exhaust jet stream F of circulation in measure and transmit pipeline 7, or through one second Acquisition channel 25, determine and send the temperature of the exhaust jet stream F of circulation in a pipeline 7 over the state of a predetermined temperature threshold.
This data processing module 40 is connected with this administration module 30, and is set to send order according to the information that is received from administration module 30 or temperature information module (10,20), to control gas emitting valve 5,5 ', 5 " in one or more opening or closing.
This data processing module 40 can comprise or be connected to a storage (not shown), and this storage is set to store computer program.Such program can be designed for process temperature information, and sends the valve 5,5 ', 5 for the gas blow-off system of aircraft " opening and closing order.
For example, for execution control function, data processing module 40 can be measured poor between the temperature that receives and a reference temperature, and makes in described valve, for example proportional action of fan gas emitting valve.
Similarly, for example, for execution monitoring function, data processing module 40 can determine whether that received measured value surpasses a threshold value, if consequently received state shows that one surpasses situation, carries out an action and closes this fan gas emitting valve.
Like this, in system according to the present invention, this administration module makes can obtain significantly temperature information and its form is set, and this data processing module makes to analyze the temperature information that is received from this administration module, and can actuate the valve of the gas blow-off system of one or more these aircraft.The action of described gas emitting valve can self be carried out by this puocessing module 40, otherwise this puocessing module can be to another module or system, for example, for monitoring the module of aircraft cabin, send an alert message, make pilot's one or more gas emitting valves of manual drives elsewhere.
According in an embodiment of system of the present invention, valve 5,5 ', 5 " can by data processing module 40 or by another module of this aircraft, for example, for the module manually being monitored by pilot, carry out telecontrol.In another embodiment, a valve, for example in the gas emitting valve depressed, can be independently, and can be for example a spring-operated pneumatic valve, this spring-operated pneumatic valve carrys out self-regulation according to the pressure of its terminal, so this data processing module is suitable for controlling another two valves.
In the first embodiment shown in Fig. 1 b, system 101 comprises the first temperature information module 110, the second temperature information module 120, administration module 130 and data processing module 140.
This first temperature information module 110 can be a temperature measurement probe for example.This second temperature information module 120 can be for example one second measuring probe or a thermocouple, and these are all well known by persons skilled in the art.
In this embodiment, this first temperature information module 110 and this second temperature information module 120 are two temperature measurement probe.Therefore this first temperature information module 110 and this second temperature information module 120 are set to measure the temperature of the exhaust jet stream F circulating in the pipeline 107 of this gas blow-off system 101.
This administration module 130 also comprises device 134, for monitoring that the temperature of exhaust jet stream surpasses the state of a predetermined temperature threshold.These adviser tools 134 are set to the treated passage 135 of the second measurement result M2 obtaining from the second probe 120 to be supplied to data processing module 140.
In the embodiment shown in Fig. 2 b, supplement by the first embodiment shown in Fig. 2 a, this system can comprise second administration module 130 ' identical with module 130, the second data processing module 140 ' identical with module 140 and that be connected with this administration module 130 ', and one the 3rd Acquisition channel 115 ' and one the 4th Acquisition channel 125 '. Module 130 and 140 and device 132 and 134 be therefore divided into two, as Acquisition channel 115 and 125.
The first administration module 130 is connected to the first temperature information module 110 on the one hand, is connected on the other hand the second temperature information module 120.
The second administration module is connected to the first temperature information module 110 by the 3rd Acquisition channel 115 ' on the one hand, is connected to the second temperature information module 120 on the other hand by the 4th Acquisition channel 125 '.
In this embodiment, this first temperature information module 110 and the second temperature information module 120 are two temperature measurement probe.
This first administration module 130 is suitable for through one first Acquisition channel 115, reception is from the first row bleed flow temperature measurement result M1 of the first measuring probe 110, and through one second Acquisition channel 125, receive the second row bleed flow temperature measurement result M2 from the second measuring probe 120.
This second administration module 130 ' is suitable for through one the 3rd Acquisition channel 115 ', reception is from the first row bleed flow temperature measurement result M1 of the first measuring probe 110, and through one the 4th Acquisition channel 125 ', receive the second row bleed flow temperature measurement result M2 from the second measuring probe 120.
This first administration module 130 comprises temperature control apparatus 132, and this temperature control apparatus 132 is set to treated passage 135, and the temperature measurement result M1 being provided by the first temperature information module 110 is supplied to data processing module 140.This data processing module 140 is this measurement result receiving with reprocessing, controls, to regulate the temperature of this air-flow F for aircraft gas emitting valve.
This first administration module 130 also comprises for monitoring that the temperature of exhaust jet stream F surpasses the device 134 of the state of a predetermined temperature threshold.This surveillance device 134 subsequently treated passage 135 is supplied to data processing module 140 by the second measurement result M2 being obtained by the second probe 120, this data processing module 140 is execution monitoring function subsequently, uses this threshold value to surpass state, makes to control or control valve 5 not, 5 ', 5 ".
Similarly, this second administration module 130 ' comprises temperature control apparatus 132 ', and this temperature control apparatus 132 ' is set to treated passage 135 ', and the temperature measurement result M1 being provided by the first temperature information module 110 is supplied to data processing module 140 '.This data processing module 140 ' is this measurement result receiving with reprocessing, for aircraft gas emitting valve 5,5 ', 5 " control, to regulate the temperature of this air-flow F.
This second administration module 130 ' also comprises for monitoring that the temperature of exhaust jet stream surpasses the device 134 ' of the state of a predetermined temperature threshold.
This surveillance device 134 ' subsequently treated passage 135 ' is supplied to data processing module 140 ' by the second measurement result M2 being obtained by the second probe 120, this data processing module 140 ' is execution monitoring function subsequently, use this threshold value to surpass state, make to control or control valve 5 not, 5 ', 5 ".
Therefore, according to this embodiment of system of the present invention, making to replace two via four Acquisition channels reports respectively by probe 110 and 120 temperature measurement result M1 and the M2 that measure.In other words, each measurement result is reported twice to different data processing modules through different Acquisition channels.Such module and passage redundancy make the reliability that can tighten control and monitor, suppose that the loss of in module can not cause two useful measurement results of control & monitor function to lose, and it is retained on another administration module.Such structure can easily realize on the computer of aircraft that is for example called " engine " computer.In fact, such known computer comprises two data processing modules, and wherein each data processing module all communicates by a physical data communication port.Administration module can be arranged on this computer, be connected on the one hand their minute other data processing modules, each administration module is connected with two probes by two passages on the other hand, these two passages are connected to one and identical probe, and this probe is on one of this computer and identical physical communication passage.
Fig. 2-6 demonstration is according to five of system of the present invention other embodiments, and still, for the sake of clarity, valve and stream F do not represent.And, the embodiment relevant to Fig. 2 a illustrated embodiment who shows as for Fig. 2 b, by each embodiment shown in Fig. 3-7 can be divided into two similar, in addition necessary change, to ensure this system.For the sake of clarity, these twice forms do not represent.
In the 3rd embodiment shown in Fig. 2, this system 201 comprises that temperature measurement probe 210, temperature threshold surpass status information module 220, administration module 230 and puocessing module 240.
Thus obtained digital value is supplied to subsequently field programmable gate array (FPGA) 260 and processes.Particularly, field programmable gate array (FPGA) 260 is set to format and comprises and be received from the digital value of analog-to-digital converter 250 and be received from the signal of the state of this information module 220, and surveys fault and mistake on described signal.
The state that surpasses a predetermined exhaust jet stream temperature threshold of being determined by information module 220 can for example take to comprise the discrete form of circuit or binary or Boolean.For example, this discrete low state (circuit is opened) can be corresponding to the gas flow temperature higher than this threshold value, and high state (circuit is closed) can be corresponding to for reaching threshold value, or vice versa.One binary outcome can be for example for example, for to be received from 0 or 1 of another information module (another computer) through a number bus.This surpass state by information module 220 be directly supplied to this field programmable gate array (FPGA) 260 for the treatment of.
In the 4th embodiment shown in Fig. 3, system 301 comprises that temperature measurement probe 310, temperature threshold surpass status information module 320, administration module 330 and data processing module 340.
This administration module 330 is connected to measuring probe 310 by the first Acquisition channel 315, and data processing module 340 is connected to information module 320 by the second Acquisition channel 325 merging in this and a process course.
Should be determined by information module 320, surpass the state of a predetermined exhaust jet stream temperature threshold, can, for example, take discrete form.Data processing module 340 is set to through this second Acquisition channel 325, from this information module 320, receives the described state that surpasses a predetermined exhaust jet stream temperature threshold.At this according in the embodiment of system of the present invention, this state by information module 320 second channel 325 through being also a process course at this be directly supplied to processor 380 for the treatment of.
Like this, on the one hand, between probe 310 and processor 380, on the other hand, the communication connection between information module 320 and processor 380 separated, makes separable acquisition thing until processor 380 that is to say, is decreased to the sharing model of processor 380.
In the 5th embodiment shown in Fig. 5, this system 401 comprises:
-temperature measurement probe 410,
-temperature threshold surpasses status information module 420,
-administration module 430,
-data processing module 440.
This analog-to-digital converter 450 is set to through first passage 415, receive from measuring probe 410 by the measured exhaust jet stream temperature measurement result of described probe 410.
And this this analog-to-digital converter 450 is set to the analog temperature measurement result that is received from temperature measurement probe 410 to be converted to digital value, it can be used by for example field programmable gate array (FPGA) or the such handling implement of processor.
Thus obtained this digital value is supplied to subsequently field programmable gate array (FPGA) 460 and processes.Particularly, this field programmable gate array (FPGA) 460 is set to format the signal that comprises digital value that this is received from analog-to-digital converter 450, and surveys fault or mistake on described signal.
This field programmable gate array (FPGA) 460 makes to process the digital value that is received from analog-to-digital converter 450.
Field programmable gate array (FPGA) 460 is sent to field programmable gate array (FPGA) 470 by thermometric digital value through one first process course 435.
Field programmable gate array (FPGA) 460 should surpass state through one second process course 435 ' and be sent to this secondary scene programmable gate array (FPGA) 452, made this measurement result of separation and this state completely, until FPGA470.
This FPGA470 guarantees the communication management between administration module 430 and processor 480 significantly.This FPGA470 is sent to processor 480 by described measurement result or state thus and processes.
In this embodiment, on the one hand between probe 410 and puocessing module 440, information module 420 makes the separable thing that obtains with the separated of communication connection between puocessing module 440 on the other hand, until data processing module 440, is decreased in other words the sharing model of data processing module 440.
In the 6th embodiment shown in Fig. 5, system 501 comprises:
-temperature measurement probe 510,
-temperature threshold surpasses status information module 520,
-administration module 530,
The-the first data processing module 540a,
The-the second data processing module 540b.
The measurement result M1 that this first data processing module 540a receives with reprocessing, for example to control described valve 5,5 ', 5 by direct or indirect transmission order or alarm " realize the valve 5,5 ', 5 to this system 501 " control.
Should be sent and by monitoring that information that module 534 receives can comprise thus temperature measurement result M2 or surpass the state of a predetermined temperature threshold, the state that should surpass a predetermined temperature threshold is such as being discrete result, the result of binary etc. by information module 520.
And, monitor that module 534 is connected with the second data processing module 540b, and be set to send received temperature information to described the second data processing module 540b.
This second data processing module 540b, with these data of reprocessing, makes for example by direct or indirect transmission order or alarm, to control the gas emitting valve of this system 501, to realize surpassing the supervision of a predetermined exhaust jet stream temperature threshold.
In this embodiment, this first data processing module 540a and the second data processing module 540b are can physics mode separated, and each data processing module includes a processor.
This first data processing module 540a and the second data processing module 540b can be through for example
the communication module 550 of type is connected, for being associated between them.
This first data processing module 540a can for example realize on the engine computer of this aircraft, that is to say foundation, this second data processing module 540b can be for example for example exclusively used on the special-purpose computer of this gas blow-off system of this aircraft or on another engine computer of this aircraft and realizes one.
In this case, administration module 530 can physically be divided into two, so that this control module 532 is directly set up on an engine computer, this supervision module 534 is directly set up on this second computer.
In this embodiment, on the one hand, between probe 510 and this first data processing module 540a, on the other hand, communication connection between this information module 520 and this second data processing module 540b separated makes can complete separated acquisition thing, therefore eliminates the sharing model between these two temperature information projects.
Or, this second data processing module 540b can be set to the second temperature information for example by communication module 550, send to the first data processing module 540a, so that this first data processing module 540a processes the second received temperature information, and for example, send to open and close the valve 5,5 ', 5 of the gas blow-off system of this aircraft " order.In the case, to the control of gas discharging temperature with to surpassing the supervision of a predetermined gas exhaust temperature threshold value, can be undertaken by the first information and its temperature information that is received from communication module 550 that only the first data processing module 540a is received from administration module 530 according to it.This makes can be by using two data processing modules separated between two computers of for example this aircraft to carry out the acquisition thing of separated these two temperature information projects, and the information that assurance is used by puocessing module 540a mutually, in the case, this sharing model is restricted to only puocessing module 540a.
In the 7th embodiment shown in Fig. 6, system 501 also comprises the 3rd data processing module 540a ', and administration module also comprises one second control module 532 '.
This second control module 532 ' is set to through a third channel 515 ', receives the exhaust jet stream F temperature measurement result M1 from and the transmission measured by this measuring probe 510 of measuring probe 510.
Control module 532 ' is communicated with the 3rd data processing module 540a ' through a process course 535a ', and is set to send received measurement result M1 to described the 3rd data processing module 540a '.
The 3rd data processing module 540a ' is with the received measurement result M1 of reprocessing, for for example by direct or indirect transmission order to control described valve 5,5 ', 5 " carry out the valve 5,5 ', 5 of control system 501 ".
This first data processing module 540a and the 3rd data processing module 540a ' can take turns flow operation, and for example one is main and active, and another is less important and passive, if so that this primary module breaks down, this less important module can be taken over.
In this embodiment, this the first data processing module 540a and the 3rd data processing module 540a ' can for example set up on an engine computer of this aircraft, this second data processing module 540b can for example set up on the special-purpose computer of gas blow-off system that is for example exclusively used in this aircraft, or sets up on another engine computer of this aircraft.
In this case, administration module 530 can physically be divided into two, so that control module 532 and 532 ' is directly set up on an engine computer, monitors that module 534 is directly upper foundation of second computer (special-purpose or not special-purpose).
When control module 532 and 532 ' comprises while setting up on the engine computer of two physical channels one, passage 515 and 515 ' can physically be based upon respectively on the first physical channel of this engine computer and on the second physical channel.
In this embodiment, on the one hand, between probe 510 and the first data processing module 540a and the 3rd data processing module 540a ', on the other hand, communication connection between information module 520 and the second data processing module 540b separated makes can complete separated acquisition thing, thereby eliminate the sharing model between this two temperatures information project completely, guarantee the acquisition of the first temperature information, to carry out this temp. control function.
Or, this second data processing module 540b can be set to the second temperature information through communication module 550, be sent to the first data processing module 540a or be sent to the 3rd data processing module 540a ', so that the first data processing module 540 or the 3rd data processing module 540 ' are processed this second temperature information of receiving, and for example send the valve 5 of the gas blow-off system open or close this aircraft, 5 ', 5 " order.
Claims (10)
1. a gas blow-off system for aircraft, described system (1,101,10,201,301,401,501) comprising:
-at least one gas emitting valve (5,5 ', 5 "), this gas emitting valve is suitable for discharging this carry-on air-flow (F),
The-the first temperature information module (10,110,210,310,410,510), this the first temperature information module is set to through one first Acquisition channel (15,115,115 ', 215,315,415,515,515 '), determine and send first row bleed flow (F) temperature information
The-the second temperature information module (20,120,220,320,420,520), this second temperature information module is set to through one second Acquisition channel (25,125,125 ', 225,325,425,525), and determine and send second row bleed flow (F) temperature information,
-at least one administration module (30,130,130 ', 230,330,430,530), this administration module and a data processing module (40,140,140 ', 240,340,440,540,540a ', 540b) is connected, and is set to:
-on the one hand, through described the first Acquisition channel (15,115,115 ', 215,315,415,515,515 '), receive described first row bleed flow temperature information, for the gas emitting valve (5,5 '; 5 of a correspondence ") control, and/or, on the other hand, through described the second Acquisition channel (25,125,125 ', 225,325,425,525), this second row bleed flow (F) temperature information makes to monitor surpassing of predetermined exhaust jet stream (F) temperature threshold
-send described the first temperature information and the second temperature information,
-at least one data processing module (40,140,140 ', 240,340,440,540,540a ', 540b), this data processing module and described administration module (30,130,130 ', 230,330,430,530) are connected, and are set to:
-through one first process course (135,135 ', 235,335,435,535a, 535a '), receive described first row bleed flow (F) temperature information, and control for the gas emitting valve of a correspondence (5,5 ', 5 "),
-through one second process course (135,135 ', 235,335,435 ', 535b), receive described second row bleed flow (F) temperature information, make to monitor to the surpassing of predetermined exhaust jet stream (F) temperature threshold, and make at least one gas emitting valve (5,5 ', 5 ") in the situation that being exceeded, described threshold value can close.
2. the gas blow-off system of aircraft according to claim 1, this the first temperature information module (10 wherein, 110, 210, 310, 410, 510) be set to through this first Acquisition channel (15, 115, 115 ', 215, 315, 415, 515, 515 '), measure and transmit one first row bleed flow temperature measurement result, this the second temperature information module (20, 120, 220, 320, 420, 520) be set to through this second Acquisition channel (25, 125, 125 ', 225, 325, 425, 525), measure and transmit one second row bleed flow temperature measurement result, or through this second Acquisition channel (25, 125, 125 ', 225, 325, 425, 525), determine and send the temperature of this exhaust jet stream (F) over the state of a predetermined temperature threshold.
3. the gas blow-off system of aircraft according to claim 1 and 2, wherein this first temperature information module (110) is set to through this first Acquisition channel (115), measure and transmit one first row bleed flow (F) temperature measurement result, this the second temperature information module (120) is set to through this second Acquisition channel (125), measure and transmit one second row bleed flow (F) temperature measurement result, this administration module (130) is suitable for from this first temperature information module (110), through this first Acquisition channel (115), receive described the first measurement result, and from this second temperature information module (120), through this second Acquisition channel (125), receive described the second measurement result, described administration module is connected with a puocessing module (140), described the first and second process course (135) are identical.
4. according to the gas blow-off system of the aircraft described in any one in aforementioned claim, described system (101 ') also comprises one second administration module (130 '), this second administration module is connected with one second data processing module (140 ') by the third and fourth same treatment passage (135 '), and on the one hand, be connected to described the first temperature information module (110), on the other hand, be connected to described the second temperature information module (120), this second administration module (130 ') is suitable for through one the 3rd Acquisition channel (115 '), from this first temperature information module (110), receive this first measurement result, and through one the 4th Acquisition channel (125 '), from this second temperature information module (120), receive this second measurement result.
5. the gas blow-off system of aircraft according to claim 1 and 2, wherein this first temperature information module (210) is set to through described the first Acquisition channel (215), measure and transmit one first row bleed flow (F) temperature measurement result, this the second temperature information module (220) is set to through described the second Acquisition channel (225), determine and send the temperature of an exhaust jet stream (F) over the state of a predetermined temperature threshold, this administration module (230) is set to through described the first Acquisition channel (215), receive this temperature measurement result, through described the second Acquisition channel (225), receive and should surpass state, this first and second process course (235) is identical.
6. the gas blow-off system of aircraft according to claim 1 and 2, wherein this first temperature information module (310) is set to through described the first Acquisition channel (315), measure and transmit one first row bleed flow (F) temperature measurement result, this the second temperature information module (320) is set to through described the second Acquisition channel (325), determine and send the temperature of an exhaust jet stream (F) over the state of a predetermined temperature threshold, this administration module (330) is set to through described the first Acquisition channel (315), receive this temperature measurement result, this data processing module (340) is set to through described the second Acquisition channel (325), receive and should surpass state, described the second Acquisition channel (325) and the second process course (325) are identical.
7. the gas blow-off system of aircraft according to claim 1 and 2, wherein this first temperature information module (410) is set to through described the first Acquisition channel (415), measure and transmit one first row bleed flow (F) temperature measurement result, this the second temperature information module (420) is set to through described the second Acquisition channel (425), determine and send the temperature of exhaust jet stream described in (F) over the state of a predetermined temperature threshold, this administration module (430) is set to through described the first Acquisition channel (415), receive described temperature measurement result, and through described the second Acquisition channel (425), receive the described state that surpasses, described the second Acquisition channel (425) and described the second process course (435 ') are different.
8. the gas blow-off system of aircraft according to claim 1 and 2, wherein this system (501) comprises one first data processing module (540a), this first data processing module is set to through described the first process course (535a), receive described the first temperature information, with one second data processing module (540b), this second data processing module is set to, through described the second process course (535b), receive described the second temperature information.
9. the gas blow-off system of aircraft according to claim 8, described system (501) also comprises one the 3rd Acquisition channel (515 ') and one the 3rd data processing module (540a '), the 3rd data processing module is set to, through one the 3rd process course (535a '), receive described the first temperature information.
10. for managing the method at the gas blow-off system of aircraft, described aircraft comprises a gas blow-off system, and described system (1,101,10,201,301,401,501) comprising:
-at least one gas emitting valve (5,5 ', 5 "), this gas emitting valve is suitable for discharging this carry-on air-flow (F),
The-the first temperature information module (10,110,210,310,410,510), this the first temperature information module is set to through one first Acquisition channel (15,115,115 ', 215,315,415,515,515 '), determine and send first row bleed flow (F) temperature information
The-the second temperature information module (20,120,220,320,420,520), this second temperature information module is set to through one second Acquisition channel (25,125,125 ', 225,325,425,525), and determine and send second row bleed flow temperature information,
-at least one administration module (30,130,130 ', 230,330,430,530), this administration module and a data processing module (40,140,140 ', 240,340,440,540,540a ', 540b) is connected, and is set to:
-on the one hand, through this first Acquisition channel (15,115,115 ', 215,315,415,515,515 '), receive this first row bleed flow (F) temperature information, for corresponding gas emitting valve (5,5 ', 5 "), control; and/or, on the other hand, through this second Acquisition channel (25,125; 125 ', 225,325,425; 525), receive this second row bleed flow (F) temperature information, make to monitor surpassing predetermined exhaust jet stream (F) temperature threshold
-send this first temperature information and this second temperature information,
-at least one data processing module (40,140,140 ', 240,340,440,540,540a ', 540b), this data processing module and described administration module (30,130,130 ', 230,330,430,530) are connected, and are set to:
-through one first process course (135,135 ', 235,335,435,535a, 535a '), receive described first row bleed flow temperature information, and control for corresponding gas emitting valve (5,5 ', 5 "),
-through one second process course (135,135 ', 235,335,435 ', 535b), receive described second row bleed flow (F) temperature information, make to monitor surpassing predetermined exhaust jet stream (F) temperature threshold, and for close at least one gas emitting valve (5 in the situation that described threshold value is exceeded, 5 ', 5 ")
The method comprises the following steps:
-at least partially in exhaust jet stream (F) on described valve,
-upper at described administration module (30,130,130 ', 230,330,430,530), receive this first temperature information from the described exhaust jet stream (F) of described the first temperature information module (10,110,210,310,410,510,610),
-at described administration module (30,130,130 ', 230,330,430,530) or described data processing module (40,140,140 ', 240,340,440,540,540a ', 540b) upper, receive from described the second temperature information module (20,120,220,320,420,520) this second temperature information of described exhaust jet stream (F)
-described data processing module (40,140,140 ', 240,340,440,540,540a ', 540b) upper, receive described the first temperature information and/or the second temperature information,
-according to described the first temperature information and/or the second temperature information, described data processing module (40,140,140 ', 240,340,440,540,540a ', 540b) upper, control opening or closing of one or more gas emitting valves (5,5 ', 5 ").
Applications Claiming Priority (3)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| FR1156494 | 2011-07-18 | ||
| FR1156494A FR2978123B1 (en) | 2011-07-18 | 2011-07-18 | SYSTEM FOR MONITORING AND MONITORING AN AIRCRAFT |
| PCT/FR2012/051596 WO2013011222A1 (en) | 2011-07-18 | 2012-07-06 | Aircraft control and monitoring system |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN103703227A true CN103703227A (en) | 2014-04-02 |
| CN103703227B CN103703227B (en) | 2016-09-14 |
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| US (1) | US9194300B2 (en) |
| EP (1) | EP2734719B1 (en) |
| JP (1) | JP5976802B2 (en) |
| CN (1) | CN103703227B (en) |
| BR (1) | BR112014001216B1 (en) |
| CA (1) | CA2841896C (en) |
| FR (1) | FR2978123B1 (en) |
| RU (1) | RU2598497C2 (en) |
| WO (1) | WO2013011222A1 (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN105667804A (en) * | 2014-11-19 | 2016-06-15 | 中国航空工业集团公司西安飞机设计研究所 | Method for calculating air feed temperature target of cabin of large airplane |
| CN106697298A (en) * | 2016-12-29 | 2017-05-24 | 东方航空技术有限公司 | Alarming method and system and monitoring terminal for aircraft |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| US9611033B1 (en) * | 2015-09-24 | 2017-04-04 | Rockwell Collins, Inc. | System and method for maintaining system integrity in control systems having multi-lane computational differences |
| US9994327B1 (en) * | 2016-12-13 | 2018-06-12 | United Technologies Corporation | Aircraft nacelle anti-ice systems and methods |
| FR3070057B1 (en) * | 2017-08-11 | 2019-09-06 | Safran Aircraft Engines | CONTROL UNIT FOR A CONTROLLED VALVE FOR SAMPLING AN AIR FLOW IN A PRESSURIZED AIR FLOW OF AN AIRCRAFT |
| FR3097963B1 (en) * | 2019-06-27 | 2021-06-04 | Liebherr Aerospace Toulouse Sas | Monitoring the state of an exchanger in an aircraft air circuit |
| US20230037115A1 (en) * | 2020-01-02 | 2023-02-02 | Lufthansa Technik Ag | Method and computer program product for monitoring a bleed air supply system of an aircraft |
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- 2012-07-06 RU RU2014103623/06A patent/RU2598497C2/en active
- 2012-07-06 WO PCT/FR2012/051596 patent/WO2013011222A1/en active Application Filing
- 2012-07-06 US US14/232,736 patent/US9194300B2/en active Active
- 2012-07-06 JP JP2014520699A patent/JP5976802B2/en active Active
- 2012-07-06 CA CA2841896A patent/CA2841896C/en active Active
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Also Published As
| Publication number | Publication date |
|---|---|
| EP2734719A1 (en) | 2014-05-28 |
| WO2013011222A1 (en) | 2013-01-24 |
| JP2014526993A (en) | 2014-10-09 |
| RU2014103623A (en) | 2015-08-27 |
| US9194300B2 (en) | 2015-11-24 |
| EP2734719B1 (en) | 2015-09-09 |
| US20140199158A1 (en) | 2014-07-17 |
| RU2598497C2 (en) | 2016-09-27 |
| BR112014001216B1 (en) | 2021-01-12 |
| CN103703227B (en) | 2016-09-14 |
| CA2841896C (en) | 2018-10-09 |
| FR2978123B1 (en) | 2013-08-23 |
| CA2841896A1 (en) | 2013-01-24 |
| JP5976802B2 (en) | 2016-08-24 |
| BR112014001216A2 (en) | 2017-02-21 |
| FR2978123A1 (en) | 2013-01-25 |
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